Influence of wall mounted ramps on DLR strut scramjet combustor under non-reacting flow field

Abstract

The scramjet technology is considered to be the advanced engine for high-speed transportations. The present numerical examination addresses the influence of double ramp's implications in the scramjet engine combustor walls accompanied by strut injection technique under non-reacting flow conditions. The numerical analyses are performed using simulation software, ANSYS Fluent 18.0. Computational problems have been modeled using Reynolds averaged Navier-Stokes (RANS) equations. The inlet flow condition of the model is Mach (Ma) 2 and sonic speed hydrogen fuel from the strut is driven along the flow direction. The characteristics of flow for the two-dimensional (2D) combustor models are studied using shadowgraph images and Mach number contours. Numerical solutions are analogized with the published experimental outcome for validation. The wall static pressure values are higher at the vicinity of the strut ramps regions due to the additional shock interactions generated from the ramps compared to the DLR scramjet model. The subsonic zones are created due to additional shock waves and enhance air–fuel mixing for ramp-mounted combustors. The total pressure loss across the combustor increases as the ramps are positioned downstream of the strut.